|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/134C ; 244/130|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 81 인용 특허 : 0|
An anti-icing system for leading edges of an aircraft. Hot compressed air is discharged from a cavity behind the leading edge, through a multitude of small holes in the leading edge skin into the airflow impinging on the leading edge. In a first embodiment the anti-icing system utilizes part of the air distribution system in existence for a laminar flow control system. Instead of sucking air into the wing, as is done in the laminar flow control mode, the flow is reversed in the anti-icing mode, blowing hot compressed air out of the wing. In a second embo...
An anti-icing apparatus for an aircraft, said apparatus comprising: a. an aircraft structure comprising a skin section with a leading edge and with a first forwardly facing leading edge surface portion which is that portion of said skin section most susceptible to icing, and a second surface portion which extends rearwardly from the first leading edge surface portion to receive air flow from said first leading edge surface portion and which is less susceptible to icing; b. said first leading edge surface portion being formed with a plurality of through a...